EP1306558A1 - Electric-hydraulic device for changing the pitch of a fan - Google Patents

Electric-hydraulic device for changing the pitch of a fan Download PDF

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Publication number
EP1306558A1
EP1306558A1 EP02292594A EP02292594A EP1306558A1 EP 1306558 A1 EP1306558 A1 EP 1306558A1 EP 02292594 A EP02292594 A EP 02292594A EP 02292594 A EP02292594 A EP 02292594A EP 1306558 A1 EP1306558 A1 EP 1306558A1
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EP
European Patent Office
Prior art keywords
piston
machine
rotor
integral
propeller
Prior art date
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Granted
Application number
EP02292594A
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German (de)
French (fr)
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EP1306558B1 (en
Inventor
Michel Franchet
Daniel Kettler
Jean-Pierre Ruis
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Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
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Publication date
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Publication of EP1306558A1 publication Critical patent/EP1306558A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F04D29/36—Blade mountings adjustable
    • F04D29/362—Blade mountings adjustable during rotation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/305—Blade pitch-changing mechanisms characterised by being influenced by other control systems, e.g. fuel supply
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/44—Blade pitch-changing mechanisms electric
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F04D29/323—Blade mountings adjustable
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a control device of pitch change using an electrohydraulic actuator. She can be applied to any system equipped with a propeller, wind turbine or industrial fan for example like turboprops and turbojets having a blower comprising a plurality of blades or blades with variable pitch angle.
  • the pitch control can also be performed by a electric drive system based on magnet motors permanent or asynchronous systems associated with screw-nut systems (see EP 0 154 808 example) or solidarity pinions of each blade (FR 89 0641 and FR 2 712 250 for example).
  • magnet motors permanent or asynchronous systems associated with screw-nut systems see EP 0 154 808 example
  • solidarity pinions of each blade FR 89 0641 and FR 2 712 250 for example
  • the present invention proposes to overcome the disadvantages of these devices of the prior art with a step control device propeller that is simple, compact and particularly reliable.
  • a goal of the invention is in particular to propose a control device which eliminates any risk of hydraulic leaks.
  • a control device electrohydraulic variation of the pitch of the blades of a rotor of a machine the blades being mounted on a shaft driven in rotation by a shaft of driving the machine and each having a pivotable foot around a longitudinal axis of the blade, the drive shaft being even driven in rotation with respect to a fixed structure of the machine, characterized in that it comprises on the one hand a hydraulic cylinder one of which piston is integral with a control ring and synchronization in which are engaged off-center crank pins fixed under each of said feet of the blades and of which a cylindrical body is closed by a lid incorporating a high pressure hydraulic pump (preferably piston) supplying hydraulic fluid to both sides of said piston through integrated channels in said cylindrical body of the cylinder and secondly a electric motor driven and powered by a generator current comprising an inductor integral with said fixed structure of the turboprop engine and an armature secured to said drive shaft of the turbine engine.
  • a high pressure hydraulic pump preferably piston
  • the current generator may be constituted by a rotating transformer or by a ring collector system smooth and brooms. It is operated by an electronic control circuit connected on the one hand to a power supply device of the machine and on the other hand to a calculator of the machine, and arranged to modulate the power supply of said electric motor provided by said device energy supply, so as to act on the time and / or the operation and direction of rotation of said high hydraulic pump pressure to obtain a determined displacement of the corresponding piston to a desired setting of the rotor blades.
  • the hydraulic cylinder comprises a linear sensor of type LVDT formed of a cylindrical tube integral with the cylindrical body of the cylinder and a plunger integral with a piston rod and can be move linearly in the tube.
  • a linear sensor of type LVDT formed of a cylindrical tube integral with the cylindrical body of the cylinder and a plunger integral with a piston rod and can be move linearly in the tube.
  • the invention is applicable both at the level of a blower of a turbojet engine than a propeller of a turboprop, a wind turbine or an industrial fan.
  • the calculator is the full authority calculator (FADEC) of the turboprop or turbojet.
  • the turboprop has a propeller comprising a plurality of blades 10 mounted on a shaft 12 driven by rotation by the main drive shaft 14 of the turboprop (via first fastening means 16), this drive shaft being same rotated against a fixed structure 18 of turboprop by a gas generator through a reduction gearbox speed (both not shown).
  • Each blade has a foot or pivot 20 movable in rotation about its longitudinal axis X.
  • the device for controlling the pitch of the propeller comprises a hydraulic cylinder whose piston 22 is secured by its rod 23 of a control and synchronization ring 24 in bores axial 26 which are engaged off-center crank pins 28 fixed under each of the blade roots and whose cylindrical body 30 is closed by a cover incorporating a high pressure hydraulic pump 32 of the type axial or radial pistons.
  • the pump supplies hydraulic fluid to both sides of the piston 22 through channels 34 integrated into the cylindrical body 30 of the cylinder. It is driven by an electric motor 36, preferably of the type asynchronous or permanent magnet, to eliminate friction and wear (thus also maintenance), controlled and supplied with current via a current generator 38 including an inductor 40 is fixed on a first support piece 42 secured to the fixed structure 18 turboprop and an armature 44 is fixed on a second support piece 46 arranged opposite the previous one and attached to the tree 14 of the turboprop.
  • an electric motor 36 preferably of the type asynchronous or permanent magnet, to eliminate friction and wear (thus also maintenance)
  • a current generator 38 including an inductor 40 is fixed on a first support piece 42 secured to the fixed structure 18 turboprop and an armature 44 is fixed on a second support piece 46 arranged opposite the previous one and attached to the tree 14 of the turboprop.
  • An electronic control circuit 48 connected on the one hand by a power link 50 to the electrical power supply device turboprop (not shown) that will deliver the power electrical power required for the current control of the electric motor and on the other hand by an electrical connection 52 to the full digital calculator Authority (or FADEC - Full Authority Digital Electronic Computer) of the turboprop (not shown) which will deliver the information of control (angle of rotation of the blade) necessary for the variation of the pitch propeller, allows modulation of the motor power supply electric according to the conditions flight of the aircraft and in function information provided by torque and speed sensors (no shown) located on the drive shaft 14 of the turboprop, how to act on the time and / or operating regime and the meaning of rotation of the hydraulic pump 32 and obtain the displacement of the piston 22 of the cylinder necessary to ensure the setting of the desired propeller blades (so the desired thrust).
  • the full digital calculator Authority or FADEC - Full Authority Digital Electronic Computer
  • a control of the angle of rotation of the blade is preferably provided by a linear sensor type LVDT (Linear Variable Differential Transformer) mounted inside the cylinder and formed of a cylindrical tube 54 secured to the body of the jack 30 and a core diver 56 secured to the piston rod 23 and movable linearly in this tube.
  • LVDT Linear Variable Differential Transformer
  • An example of such a sensor is given in the European Patent Application EP1 081 390.
  • To the displacement of the core in the tube corresponds an electrical output signal delivered to the calculator by the LVDT sensor and representative of the position of the rod of the cylinder, itself proportional to the angle of rotation of the blade.
  • the displacement sensor is of the redundant type with two independent output signals.
  • the current supply means can be constituted by a conventional system with a smooth ring collector armature) mounted on the second support piece 46 and secured to the shaft 14 and brushes (acting as inductor) mounted on the first support piece 42 and integral with the fixed structure 18.
  • These means may also preferably be made by a transformer rotating having an inductive coil mounted on the first piece support 42 and secured to the fixed structure 18 and an induced coil mounted on the second support piece 46 and secured to the shaft 14, thereby forming a current generator.
  • control device The operation of the control device according to the invention is schematically the following.
  • the control device is actuated when, during a phase of flight of the aircraft, the pilot wishes in particular to modify the thrust of his device.
  • the FADEC will send to the electronic circuit of command an order that will generate an excitation current in the inductor of the generator that will create an electric field in the armature located opposite and rotated by the drive shaft of the propeller. This electric field transformed into a current in the armature of the generator will then directly power the electric motor.
  • the excitation current is more or less modulated to vary the field magnetic and therefore the speed of the electric motor, which will act to his turn on the speed of the hydraulic pump.
  • the inductor as the generator of the current generator are preferably each constituted two pairs of concentric coils energized separately for each direction of rotation.
  • the hydraulic fluid present in the pump 32 and which is alternatively sucked on one face of the piston 22 and discharged on the other face circulates as for him in closed circuit in the assembly pump-cylinder, the fluid volume variations due to compressibility or dilation being compensated classically by an accumulator 58 integrated in this high pressure hydraulic pump.
  • an accumulator 58 integrated in this high pressure hydraulic pump.
  • At a high rotation rate of electric motor corresponds to a high movement speed of the piston, the operating time ensuring the length of the displacement, therefore the value of the calibration.
  • the assembly formed by the hydraulic pump and the electric motor can to be advantageously replaced by an integrated piston electric pump, the pump barrel then serving as a rotor (preferably magnets permanent or asynchronous).
  • the electropump and the accumulator are arranged in the axis of the cylinder of to obtain perfect axial symmetry, which allows a training unbalanced or at least easy to balance.

Abstract

The device has a hydraulic actuator with a piston, and a cylinder (30) with high pressure hydraulic pump (32). The piston is secured to control and synchronization ring in which off-center wrist pins are fixed in blade roots. A hydraulic fluid from the pump is fed to the piston via channel (34). An electric motor (36) with an inductor and an armature is controlled and powered by an electricity generator (38).

Description

Domaine de l'inventionField of the invention

La présente invention se rapporte à un dispositif de commande de changement de pas d'hélice utilisant un actionneur électrohydraulique. Elle trouve application à tout système muni d'une hélice, éolienne ou ventilateur industriel par exemple, comme aux turbopropulseurs et turboréacteurs munis d'une soufflante comprenant une pluralité d'aubes ou de pales à angle de calage variable.The present invention relates to a control device of pitch change using an electrohydraulic actuator. She can be applied to any system equipped with a propeller, wind turbine or industrial fan for example like turboprops and turbojets having a blower comprising a plurality of blades or blades with variable pitch angle.

Art antérieurPrior art

Il est connu, pour augmenter les performances et améliorer le rendement du moteur d'une turbomachine durant toutes les phases de son fonctionnement, du décollage à l'atterrissage, de recourir à la variation du pas d'hélice ou de soufflante. Ce calage variable permet en outre de faire varier le régime de l'hélice ou de la soufflante pour obtenir la poussée désirée, sans modifier celui de la turbine qui est en général calé à son régime maximum continu, voire, lors de l'atterrissage, d'inverser cette poussée remplaçant ainsi les systèmes conventionnels lourds et complexes d'inversion de poussée.It is known, to increase performance and improve the engine performance of a turbomachine during all phases of its operation, from take-off to landing, to resort to variation pitch of propeller or blower. This variable setting also makes it possible to vary the speed of the propeller or blower to obtain the desired thrust, without modifying that of the turbine, which is usually set at its maximum continuous regime, or even, during the landing, to reverse this thrust thus replacing the conventional heavy and complex systems reverse thrust.

Les dispositifs actuels de commande de variation de pas d'hélice comporte généralement des actionneurs hydrauliques (vérin entraínant chaque pied d'aube) qui procurent la force nécessaire pour placer l'hélice dans la position désirée. Ces dispositifs sont toutefois particulièrement complexes, encombrants et présentent en outre des problèmes importants de fiabilité dus notamment à l'utilisation de joints ou de raccords tournants. En effet, il est important d'éviter toute fuite du fluide hydraulique vers la turbine source de dégradation des performances, voire même d'incendie et de limiter tout risque de pollution (contamination des prélèvements d'air). Le brevet US 5,897,293 illustre parfaitement ce type de dispositif hydraulique comportant de très nombreuses tuyauteries, des valves hydrauliques et des joints tournants qu'il est nécessaire de faire cheminer ou de loger au travers du corps et de l'arbre d'entraínement de la turbomachine.Current propeller pitch variation control devices generally comprises hydraulic actuators (actuating cylinder each dawn foot) that provide the necessary force to place the propeller in the desired position. These devices are however particularly complex, cumbersome and have significant problems of reliability due in particular to the use of joints or fittings turns. Indeed, it is important to avoid any fluid leakage hydraulics towards the turbine, a source of performance degradation, even of fire and to limit any risk of pollution (contamination of air sampling). US Pat. No. 5,897,293 perfectly illustrates this type hydraulic device comprising a large number of pipes, hydraulic valves and rotary joints that it is necessary to make walk or lodge through the body and the drive shaft of the turbomachine.

La commande de pas d'hélice peut aussi être réalisée par un système électrique d'entraínement à base de moteurs à aimants permanents ou asynchrones associés à des systèmes vis-écrou (voir par exemple EP 0 154 808) ou à des pignons solidaires de chaque aube (FR 89 0641 et FR 2 712 250 par exemple). Toutefois, de tels systèmes impliquent le recours à des moteurs volumineux pour assurer les fortes puissances nécessaires aux déplacements rapides du pas de l'hélice sans trop démultiplier le mécanisme de calage.The pitch control can also be performed by a electric drive system based on magnet motors permanent or asynchronous systems associated with screw-nut systems (see EP 0 154 808 example) or solidarity pinions of each blade (FR 89 0641 and FR 2 712 250 for example). However, such systems involve the use of bulky engines to ensure the strong powers necessary for rapid movements of the pitch of the propeller without To increase the setting mechanism too much.

Objet et définition de l'inventionObject and definition of the invention

La présente invention propose de pallier les inconvénients de ces dispositifs de l'art antérieur avec un dispositif de commande de pas d'hélice qui soit simple, peu encombrant et particulièrement fiable. Un but de l'invention est notamment de proposer un dispositif de commande qui élimine tout risque de fuites hydrauliques.The present invention proposes to overcome the disadvantages of these devices of the prior art with a step control device propeller that is simple, compact and particularly reliable. A goal of the invention is in particular to propose a control device which eliminates any risk of hydraulic leaks.

Ces buts sont atteints par un dispositif de commande électrohydraulique de variation du pas des pales d'un rotor d'une machine, les pales étant montées sur un fût entraíné en rotation par un arbre d'entraínement de la machine et ayant chacune un pied pouvant pivoter autour d'un axe longitudinal de la pale, l'arbre d'entraínement étant lui même entraíné en rotation par rapport à une structure fixe de la machine, caractérisé en ce qu'il comporte d'une part un vérin hydraulique dont un piston est solidaire d'un anneau de commande et de synchronisation dans lequel sont engagés des manetons décentrés fixés sous chacun desdits pieds des pales et dont un corps cylindrique est fermé par un couvercle intégrant une pompe hydraulique haute pression (de préférence à pistons) alimentant en fluide hydraulique les deux faces dudit piston au travers de canaux intégrés dans ledit corps cylindrique du vérin et d'autre part un moteur électrique commandé et alimenté en courant par une génératrice de courant comportant un inducteur solidaire de ladite structure fixe du turbopropulseur et un induit solidaire dudit arbre d'entraínement de la turbomachine.These goals are achieved by a control device electrohydraulic variation of the pitch of the blades of a rotor of a machine, the blades being mounted on a shaft driven in rotation by a shaft of driving the machine and each having a pivotable foot around a longitudinal axis of the blade, the drive shaft being even driven in rotation with respect to a fixed structure of the machine, characterized in that it comprises on the one hand a hydraulic cylinder one of which piston is integral with a control ring and synchronization in which are engaged off-center crank pins fixed under each of said feet of the blades and of which a cylindrical body is closed by a lid incorporating a high pressure hydraulic pump (preferably piston) supplying hydraulic fluid to both sides of said piston through integrated channels in said cylindrical body of the cylinder and secondly a electric motor driven and powered by a generator current comprising an inductor integral with said fixed structure of the turboprop engine and an armature secured to said drive shaft of the turbine engine.

Cette structure conduit à un dispositif de commande très simplifié, particulièrement compact et facile à mettre en oeuvre. Les risques de fuites sont fortement limitées du fait de l'absence de tuyauteries et de raccords tournants.This structure leads to a very simplified control device, particularly compact and easy to implement. The risks of leakage is severely limited due to the lack of piping and rotating fittings.

La génératrice de courant peut être constituée par un transformateur tournant ou bien par un système à collecteur à bagues lisses et balais. Elle est actionnée par un circuit électronique de commande relié d'une part à un dispositif d'alimentation en énergie de la machine et d'autre part à un calculateur de la machine, et agencé pour moduler l'alimentation en courant dudit moteur électrique fournie par ledit dispositif d'alimentation en énergie, de façon à agir sur le temps et/ou le régime de fonctionnement et le sens de rotation de ladite pompe hydraulique haute pression pour obtenir un déplacement déterminé du piston correspondant à un calage désiré des pales du rotor.The current generator may be constituted by a rotating transformer or by a ring collector system smooth and brooms. It is operated by an electronic control circuit connected on the one hand to a power supply device of the machine and on the other hand to a calculator of the machine, and arranged to modulate the power supply of said electric motor provided by said device energy supply, so as to act on the time and / or the operation and direction of rotation of said high hydraulic pump pressure to obtain a determined displacement of the corresponding piston to a desired setting of the rotor blades.

De préférence, le vérin hydraulique comporte un capteur linéaire de type LVDT formé d'un tube cylindrique solidaire du corps cylindrique du vérin et d'un noyau plongeur solidaire d'une tige du piston et pouvant se déplacer linéairement dans le tube.Preferably, the hydraulic cylinder comprises a linear sensor of type LVDT formed of a cylindrical tube integral with the cylindrical body of the cylinder and a plunger integral with a piston rod and can be move linearly in the tube.

L'invention trouve application aussi bien au niveau d'une soufflante d'un turboréacteur que d'une hélice d'un turbopropulseur, d'une éolienne ou d'un ventilateur industriel. Avantageusement, dans le domaine aéronautique, le calculateur est le calculateur pleine autorité (FADEC) du turbopropulseur ou du turboréacteur.The invention is applicable both at the level of a blower of a turbojet engine than a propeller of a turboprop, a wind turbine or an industrial fan. Advantageously, in the field aeronautics, the calculator is the full authority calculator (FADEC) of the turboprop or turbojet.

Brève description des dessinsBrief description of the drawings

Les caractéristiques et avantages de la présente invention ressortiront mieux de la description suivante, faite à titre indicatif et non limitatif, en regard de la figure unique représentant une coupe partielle axiale de l'avant d'un turbopropulseur comportant un dispositif de commande de pas d'hélice selon l'invention.The features and advantages of the present invention better from the following description, which is indicative and not limiting, opposite the single figure showing a partial section axial axis of the front of a turboprop having a pitch control of the propeller according to the invention.

Description détaillée d'un mode de réalisation préférentielDetailed description of a preferred embodiment

Dans l'exemple illustré, le turbopropulseur comporte une hélice comprenant une pluralité de pales 10 montées sur un fût 12 entraíné en rotation par l'arbre principal d'entraínement 14 du turbopropulseur (via des premiers moyens de fixation 16), cet arbre d'entraínement étant lui même entraíné en rotation par rapport à une structure fixe 18 du turbopropulseur par un générateur de gaz au travers d'un réducteur de vitesse (l'un et l'autre non représentés). Chaque pale comporte un pied ou pivot 20 mobile en rotation autour de son axe longitudinal X.In the illustrated example, the turboprop has a propeller comprising a plurality of blades 10 mounted on a shaft 12 driven by rotation by the main drive shaft 14 of the turboprop (via first fastening means 16), this drive shaft being same rotated against a fixed structure 18 of turboprop by a gas generator through a reduction gearbox speed (both not shown). Each blade has a foot or pivot 20 movable in rotation about its longitudinal axis X.

Selon l'invention, le dispositif de commande du pas d'hélice comporte un vérin hydraulique dont le piston 22 est solidaire par sa tige 23 d'un anneau de commande et de synchronisation 24 dans des alésages axiaux 26 duquel sont engagés des manetons décentrés 28 fixés sous chacun des pieds des pales et dont le corps cylindrique 30 est fermé par un couvercle intégrant une pompe hydraulique haute pression 32 du type à pistons axiaux ou radiaux.According to the invention, the device for controlling the pitch of the propeller comprises a hydraulic cylinder whose piston 22 is secured by its rod 23 of a control and synchronization ring 24 in bores axial 26 which are engaged off-center crank pins 28 fixed under each of the blade roots and whose cylindrical body 30 is closed by a cover incorporating a high pressure hydraulic pump 32 of the type axial or radial pistons.

La pompe alimente en fluide hydraulique les deux faces du piston 22 au travers de canaux 34 intégrés dans le corps cylindrique 30 du vérin. Elle est entraínée par un moteur électrique 36, de préférence du type asynchrone ou à aimants permanents, pour éliminer le frottement et l'usure (donc aussi la maintenance), commandé et alimenté en courant par l'intermédiaire d'une génératrice de courant 38 dont un inducteur 40 est fixé sur une première pièce support 42 solidaire de la structure fixe 18 du turbopropulseur et un induit 44 est fixé sur une seconde pièce support 46 disposée en regard de la précédente et solidaire de l'arbre d'entraínement 14 du turbopropulseur.The pump supplies hydraulic fluid to both sides of the piston 22 through channels 34 integrated into the cylindrical body 30 of the cylinder. It is driven by an electric motor 36, preferably of the type asynchronous or permanent magnet, to eliminate friction and wear (thus also maintenance), controlled and supplied with current via a current generator 38 including an inductor 40 is fixed on a first support piece 42 secured to the fixed structure 18 turboprop and an armature 44 is fixed on a second support piece 46 arranged opposite the previous one and attached to the tree 14 of the turboprop.

Un circuit électronique de commande 48, relié d'une part par une liaison de puissance 50 au dispositif d'alimentation en énergie électrique du turbopropulseur (non représenté) qui va délivrer la puissance électrique nécessaire à la commande en courant du moteur électrique et d'autre part par une liaison électrique 52 au calculateur numérique pleine autorité (ou FADEC - Full Authority Digital Electronic Computer) du turbopropulseur (non représenté) qui va délivrer les informations de commande (angle de rotation de la pale) nécessaires à la variation du pas d'hélice, permet une modulation de l'alimentation en courant du moteur électrique selon les conditions vol de l'aéronef et en fonction d'informations fournies par des capteurs de couple et de régime (non représentés) situés sur l'arbre d'entraínement 14 du turbopropulseur, de façon à agir sur le temps et/ou le régime de fonctionnement et le sens de rotation de la pompe hydraulique 32 et obtenir le déplacement du piston 22 du vérin nécessaire pour assurer le calage des pales d'hélice désiré (donc la poussée désirée). Un contrôle de l'angle de rotation de la pale est de préférence assuré par un capteur linéaire de type LVDT (Linear Variable Differential Transformer) monté à l'intérieur du vérin et formé d'un tube cylindrique 54 solidaire du corps du vérin 30 et d'un noyau plongeur 56 solidaire de la tige du piston 23 et pouvant se déplacer linéairement dans ce tube. Un exemple d'un tel capteur est donné dans la demande de brevet européen EP1 081 390. Au déplacement du noyau dans le tube correspond un signal de sortie électrique délivré au calculateur par le capteur LVDT et représentatif de la position de la tige du vérin, elle même proportionnelle à l'angle de rotation de la pale. De préférence, le capteur de déplacement est du type redondant à deux signaux de sortie indépendants.An electronic control circuit 48, connected on the one hand by a power link 50 to the electrical power supply device turboprop (not shown) that will deliver the power electrical power required for the current control of the electric motor and on the other hand by an electrical connection 52 to the full digital calculator Authority (or FADEC - Full Authority Digital Electronic Computer) of the turboprop (not shown) which will deliver the information of control (angle of rotation of the blade) necessary for the variation of the pitch propeller, allows modulation of the motor power supply electric according to the conditions flight of the aircraft and in function information provided by torque and speed sensors (no shown) located on the drive shaft 14 of the turboprop, how to act on the time and / or operating regime and the meaning of rotation of the hydraulic pump 32 and obtain the displacement of the piston 22 of the cylinder necessary to ensure the setting of the desired propeller blades (so the desired thrust). A control of the angle of rotation of the blade is preferably provided by a linear sensor type LVDT (Linear Variable Differential Transformer) mounted inside the cylinder and formed of a cylindrical tube 54 secured to the body of the jack 30 and a core diver 56 secured to the piston rod 23 and movable linearly in this tube. An example of such a sensor is given in the European Patent Application EP1 081 390. To the displacement of the core in the tube corresponds an electrical output signal delivered to the calculator by the LVDT sensor and representative of the position of the rod of the cylinder, itself proportional to the angle of rotation of the blade. Of preferably, the displacement sensor is of the redundant type with two independent output signals.

Les moyens d'alimentation en courant peuvent être constitués par un système classique avec un collecteur à bagues lisses (faisant fonction d'induit) monté sur la seconde pièce support 46 et solidaire de l'arbre d'entraínement 14 et des balais (faisant fonction d'inducteur) montés sur la première pièce support 42 et solidaires de la structure fixe 18. Ces moyens peuvent aussi de préférence être réalisés par un transformateur tournant comportant une bobine inductrice montée sur la première pièce support 42 et solidaire de la structure fixe 18 et une bobine induite montée sur la seconde pièce support 46 et solidaire de l'arbre d'entraínement 14, formant ainsi une génératrice de courant.The current supply means can be constituted by a conventional system with a smooth ring collector armature) mounted on the second support piece 46 and secured to the shaft 14 and brushes (acting as inductor) mounted on the first support piece 42 and integral with the fixed structure 18. These means may also preferably be made by a transformer rotating having an inductive coil mounted on the first piece support 42 and secured to the fixed structure 18 and an induced coil mounted on the second support piece 46 and secured to the shaft 14, thereby forming a current generator.

Le fonctionnement du dispositif de commande selon l'invention est schématiquement le suivant.The operation of the control device according to the invention is schematically the following.

Le dispositif de commande est actionné lorsque, durant une phase de vol de l'aéronef, le pilote souhaite notamment modifier la poussée de son appareil. Pour ce faire, le FADEC va adresser au circuit électronique de commande un ordre qui va générer un courant d'excitation dans l'inducteur de la génératrice qui va créer un champ électrique dans l'induit situé en regard et entraíné en rotation par l'arbre d'entraínement de l'hélice. Ce champ électrique transformé en courant dans l'induit de la génératrice va alors alimenter directement le moteur électrique. Le courant d'excitation est plus ou moins modulé pour faire varier le champ magnétique et donc le régime du moteur électrique, lequel va agir à son tour sur le régime de la pompe hydraulique. De façon à pouvoir entraíner le moteur électrique dans un sens ou dans l'autre, l'inducteur comme l'induit de la génératrice de courant sont de préférence constitués chacun de deux paires de bobines concentriques excitées séparément pour chaque sens de rotation.The control device is actuated when, during a phase of flight of the aircraft, the pilot wishes in particular to modify the thrust of his device. To do this, the FADEC will send to the electronic circuit of command an order that will generate an excitation current in the inductor of the generator that will create an electric field in the armature located opposite and rotated by the drive shaft of the propeller. This electric field transformed into a current in the armature of the generator will then directly power the electric motor. The excitation current is more or less modulated to vary the field magnetic and therefore the speed of the electric motor, which will act to his turn on the speed of the hydraulic pump. In order to be able to train the electric motor in one way or the other, the inductor as the generator of the current generator are preferably each constituted two pairs of concentric coils energized separately for each direction of rotation.

Le fluide hydraulique présent dans la pompe 32 et qui est alternativement aspiré sur une face du piston 22 et refoulé sur l'autre face circule quant à lui en circuit fermé dans l'ensemble pompe-vérin, les variations de volume du fluide dues à sa compressibilité ou sa dilatation étant compensées classiquement par un accumulateur 58 intégré à cette pompe hydraulique haute pression. A un régime de rotation élevé du moteur électrique correspond une vitesse de déplacement élevée du piston, le temps de fonctionnement assurant la longueur du déplacement, donc la valeur du calage. The hydraulic fluid present in the pump 32 and which is alternatively sucked on one face of the piston 22 and discharged on the other face circulates as for him in closed circuit in the assembly pump-cylinder, the fluid volume variations due to compressibility or dilation being compensated classically by an accumulator 58 integrated in this high pressure hydraulic pump. At a high rotation rate of electric motor corresponds to a high movement speed of the piston, the operating time ensuring the length of the displacement, therefore the value of the calibration.

On notera que, pour gagner encore en masse et en encombrement, l'ensemble formé par la pompe hydraulique et le moteur électrique peut être avantageusement remplacé par une électropompe à pistons intégrée, le barillet de pompe servant alors de rotor (de préférence à aimants permanents ou asynchrone). En outre, tous les composants de l'électropompe et de l'accumulateur sont disposés dans l'axe du vérin de façon à obtenir une parfaite symétrie axiale, ce qui permet un entraínement sans balourd ou à tout le moins facile à équilibrer.It will be noted that, in order to gain even more weight and bulk, the assembly formed by the hydraulic pump and the electric motor can to be advantageously replaced by an integrated piston electric pump, the pump barrel then serving as a rotor (preferably magnets permanent or asynchronous). In addition, all components of the electropump and the accumulator are arranged in the axis of the cylinder of to obtain perfect axial symmetry, which allows a training unbalanced or at least easy to balance.

Cette simplification du cheminement des commandes associée à la compacité du dispositif de commande selon l'invention, en libérant de l'espace dans le corps de la turbomachine, offre en outre l'opportunité de reconsidérer totalement la structure du moteur (carter, réducteur, arbre d'hélice par exemple) et donc de procurer des gains en masse et en coût supplémentaires.This simplification of the order flow associated with the compactness of the control device according to the invention, by releasing space in the body of the turbomachine, also offers the opportunity to completely reconsider the structure of the engine (crankcase, gearbox, shaft propeller for example) and thus to provide gains in mass and cost additional.

Avec l'invention, l'accès à la pompe hydraulique et au moteur électrique d'entraínement (ou à l'électropompe intégrée) est facile et rapide, du fait de sa construction modulaire, ce qui facilite la maintenance (contrôle ou dépose) tout en en réduisant son coût. De plus, si l'alimentation par transformateur tournant s'avère relativement plus complexe, elle présente l'avantage de s'effectuer sans frottement et donc sans usure au contraire d'une alimentation par collecteurs et balais, de structure plus simple, et qui présente également l'intérêt d'être plus légère en terme de masse. On notera toutefois, à l'avantage de cette seconde solution, que la vitesse de rotation des hélices, par exemple dans un gros turbopropulseur, est relativement faible (entre 1000 à 1500tr/mn) et donc l'usure en principe réduite. Notons encore que, par sécurité, on peut aussi doubler le nombre de balais.With the invention, access to the hydraulic pump and the engine electric drive (or integrated electropump) is easy and fast, because of its modular construction, which facilitates maintenance (control or removal) while reducing its cost. Moreover, if rotary transformer power supply is relatively more complex, it has the advantage of being carried out without friction and therefore wear-free, unlike a collector and broom feed, simpler structure, which also has the advantage of being lighter in terms of mass. Note, however, to the advantage of this second solution, that the speed of rotation of the propellers, for example in a big turboprop engine, is relatively low (between 1000 and 1500 rpm) and therefore wear in principle reduced. Note also that, for safety reasons, we can also double the number of brooms.

Claims (12)

Dispositif de commande électrohydraulique de variation du pas des pales d'un rotor d'une machine, les pales (10) étant montées sur un fût (12) entraíné en rotation par un arbre d'entraínement de la machine (14) et ayant chacune un pied (20) pouvant pivoter autour d'un axe longitudinal de la pale, l'arbre d'entraínement étant lui même entraíné en rotation par rapport à une structure fixe de la machine (18), caractérisé en ce qu'il comporte d'une part un vérin hydraulique dont un piston (22) est solidaire d'un anneau de commande et de synchronisation (24) dans lequel sont engagés des manetons décentrés (28) fixés sous chacun desdits pieds des pales et dont un corps cylindrique (30) est fermé par un couvercle intégrant une pompe hydraulique haute pression (32) alimentant en fluide hydraulique les deux faces dudit piston au travers de canaux (34) intégrés dans ledit corps cylindrique du vérin et d'autre part un moteur électrique (36) commandé et alimenté en courant par une génératrice de courant (38a, 38b) comportant un inducteur (40) solidaire de ladite structure fixe de la machine et un induit (44) solidaire dudit arbre d'entraínement de la machine.An electrohydraulic control device for varying the pitch of the blades of a rotor of a machine, the blades (10) being mounted on a shaft (12) driven in rotation by a drive shaft of the machine (14) and having each a foot (20) pivotable about a longitudinal axis of the blade, the drive shaft being itself rotated relative to a fixed structure of the machine (18), characterized in that it comprises d on the one hand a hydraulic cylinder with a piston (22) is integral with a control ring and synchronization (24) in which are engaged off-center pins (28) fixed under each of said blade feet and a cylindrical body (30). ) is closed by a cover incorporating a high-pressure hydraulic pump (32) supplying hydraulic fluid to both sides of said piston through channels (34) integrated in said cylindrical body of the cylinder and on the other hand an electric motor (36) controlled and fed neck rant by a current generator (38a, 38b) having an inductor (40) integral with said fixed structure of the machine and an armature (44) integral with said drive shaft of the machine. Dispositif selon la revendication 1, caractérisé en ce que ladite génératrice de courant est actionnée par un circuit électronique de commande (48) relié d'une part à un dispositif d'alimentation en énergie de la machine et d'autre part à un calculateur de la machine.Device according to Claim 1, characterized in that the said current generator is actuated by an electronic control circuit (48) connected on the one hand to a power supply device of the machine and on the other hand to a power calculator. the machine. Dispositif selon la revendication 2, caractérisé en ce que ledit circuit électronique est agencé pour moduler l'alimentation en courant dudit moteur électrique fournie par ledit dispositif d'alimentation en énergie, de façon à agir sur le temps et/ou le régime de fonctionnement et le sens de rotation de ladite pompe hydraulique haute pression pour obtenir un déplacement déterminé du piston correspondant à un calage désiré des pales du rotor. Device according to claim 2, characterized in that said electronic circuit is arranged to modulate the power supply of said electric motor provided by said power supply device, so as to act on the time and / or the operating regime and the direction of rotation of said high pressure hydraulic pump to obtain a determined displacement of the piston corresponding to a desired setting of the rotor blades. Dispositif selon la revendication 3, caractérisé en ce que ladite pompe hydraulique à haute pression est du type à pistons axiaux ou radiaux.Device according to claim 3, characterized in that said high pressure hydraulic pump is of axial piston or radial type. Dispositif selon la revendication 1, caractérisé en ce que ladite génératrice de courant est constituée par un transformateur tournant.Device according to claim 1, characterized in that said current generator is constituted by a rotating transformer. Dispositif selon la revendication 1, caractérisé en ce que ladite génératrice de courant est constituée par un système à collecteur à bagues lisses et balais.Device according to claim 1, characterized in that said current generator is constituted by a collector system with smooth rings and brushes. Dispositif selon la revendication 1, caractérisé en ce que ledit vérin hydraulique comporte un capteur linéaire de type LVDT formé d'un tube cylindrique (54) solidaire dudit corps cylindrique du vérin et d'un noyau plongeur (56) solidaire d'une tige (23) du piston et pouvant se déplacer linéairement dans ledit tube.Device according to claim 1, characterized in that said hydraulic cylinder comprises a linear sensor of the LVDT type formed of a cylindrical tube (54) integral with said cylindrical body of the jack and a plunger core (56) integral with a rod ( 23) of the piston and can move linearly in said tube. Dispositif selon la revendication 1, caractérisé en ce que ledit rotor est une hélice d'un turbopropulseur.Device according to claim 1, characterized in that said rotor is a propeller of a turboprop. Dispositif selon la revendication 1, caractérisé en ce que ledit rotor est une soufflante d'un turboréacteur.Device according to claim 1, characterized in that said rotor is a fan of a turbojet engine. Dispositif selon la revendication 8 ou la revendication 9, caractérisé en ce que ledit calculateur est le calculateur pleine autorité (FADEC) du turbopropulseur ou du turboréacteur.Device according to claim 8 or claim 9, characterized in that said computer is the full authority computer (FADEC) of the turboprop or turbojet engine. Dispositif selon la revendication 1, caractérisé en ce que ledit rotor est une hélice d'une éolienne.Device according to claim 1, characterized in that said rotor is a propeller of a wind turbine. Dispositif selon la revendication 1, caractérisé en ce que ledit rotor est une hélice d'un ventilateur industriel.Device according to claim 1, characterized in that said rotor is a propeller of an industrial fan.
EP02292594A 2001-10-24 2002-10-21 Electric-hydraulic device for changing the pitch of a fan Expired - Lifetime EP1306558B1 (en)

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FR0113715A FR2831225B1 (en) 2001-10-24 2001-10-24 ELECTROHYDRAULIC DEVICE FOR CHANGING PROPELLER PITCH
FR0113715 2001-10-24

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CN106523408A (en) * 2017-01-11 2017-03-22 温岭市威利玛机电有限公司 Large-sized industrial fan integrating motor and fan blades
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WO2022189746A1 (en) * 2021-03-09 2022-09-15 Safran Aircraft Engines Device for setting the pitch of blades for a turbine engine, and turbine engine comprising same
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WO2022248800A1 (en) * 2021-05-28 2022-12-01 Safran Aircraft Engines Electrohydraulic pitch setting with reversible pump
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FR3123314A1 (en) * 2021-05-28 2022-12-02 Safran Aircraft Engines Electro-hydraulic pitch setting with reversible pump
FR3123312A1 (en) * 2021-05-28 2022-12-02 Safran Aircraft Engines Feathering of the electro-hydraulic system with pump by valves in the rotary reference

Also Published As

Publication number Publication date
FR2831225B1 (en) 2004-01-02
FR2831225A1 (en) 2003-04-25
EP1306558B1 (en) 2006-12-13
DE60216700D1 (en) 2007-01-25
DE60216700T2 (en) 2007-10-04
US6767187B2 (en) 2004-07-27
US20030077173A1 (en) 2003-04-24

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